Leo lb-1a satellite launch system

ABSTRACT

The present invention, LB-1A, is a system for launching satellites, including small-sats, mini-sats, nano-sats, medical and scientific experiments, sub-orbital, orbital, and other aerospace payloads, which includes a modified existing carrier aircraft and a streamlined, unmanned rocket propelled lifting body spacecraft, air-launched from said carrier aircraft.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application claims the priority date of Provisional Patent Application 62/082,450 filed Nov. 20, 2014.

BACKGROUND OF THE INVENTION

Satellites are essential for many aspects of modern life. GPS, television, broadcast, mobile communications devices, all rely on the ability to place satellites in orbit.

Following advances in engineering and technology, particularly in miniaturization, the lack of an affordable, reliable and easily accessible launch service for small satellites has all but grounded flight-ready experiments and generally stifled progress in the field for several years. Having commissioned a study in summer, 2014, “Air Launch or Ground Launch: A Small Satellite Comparative Study”, to discover the reasons for this lapse, the inventors have undertaken to outline a specific air launch response. The concept of air launching space vehicles is well known through the NASA/Dryden B-52 at Edwards AFB in California, and the American space initiative largely owes its evolution to the X-15 and the Space Shuttle, both developed with data from air launched operations.

While avoiding many vagaries (uncertain weather, scheduling conflicts, flight irregularities, restrictive and expensive protocols, etc.) associated with ground based operations, the delays, high price tags and insurance costs nevertheless remain problematic. We learned from the study that air launching has challenges of its own; the negative impact on the performance of the “pitch-up” maneuver immediately after horizontal separation is far from trivial. Essentially, on release, the vehicle develops negative vertical delta-V. However, the burn rate of rocket fuels is very rapid, generally around one minute or a few seconds longer, therefore considerable first stage energy is depleted in regaining lost altitude and establishing a positive climb profile. Additionally, while rocket aerodynamics are very low drag, they are also very low lift.

BRIEF SUMMARY OF THE INVENTION

It is the intention of the inventors to utilize the information from the previously commissioned study to design and develop a system including a spacecraft and a carrier aircraft to air launch said spacecraft specifically to enable the affordable and reliable launch of small satellites and other light aerospace payloads as a service to the small-sat industry.

The present invention is a system for launching satellites, including small-sats, mini-sats, nano-sats, medical and scientific experiments, suborbital, orbital and other aerospace payloads, which includes a modified and optimized existing carrier aircraft, a streamlined, unmanned, rocket-propelled lifting body spacecraft, air launched from said carrier aircraft and containing in addition to its own propulsion, the payload, staging, and insertion rocketry necessary to the mission and provisions for protecting such payload while loading, fueling, transit to and mating with the carrier aircraft, towing, taxiing, conventional takeoff from the ground, climb and cruise to the selected launch point (LP) and high altitude orbital injection, as well as tracking, navigation and control hardware, software and other equipment necessary to establish a safe, reliable and affordable small-sat delivery service.

BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE INVENTION

FIG. 1. is an exterior plan view of the LB-1 spacecraft of the present invention.

FIG. 2. is an exterior elevation view of the LB-1 spacecraft of the present invention.

FIG. 3. is a front exterior view of the LB-1 spacecraft of the present invention.

FIG. 4. is a detail plan view of the LB-1 spacecraft of the present invention.

FIG. 5. is a detail elevation view of the LB-1 spacecraft of the present invention.

FIG. 6. is a section at line A-A of the LB-1 spacecraft of the present invention.

FIG. 7. is a plan view of conventional booster detail of the LB-1 of the present invention.

FIG. 8. is a plan view of positioning and attachment of the said LB-1 spacecraft of the present invention.

DETAILED DESCRIPTION OF THE INVENTION

All illustrations of the drawings are for the purpose of describing selected versions of the present invention and are not intended to limit the scope of the present invention.

The present invention is a system for launching satellites, including small-sats, mini-sats, nano-sats, medical and scientific experiments, suborbital, orbital and other aerospace payloads, including a modified and optimized existing carrier aircraft, a streamlined, unmanned rocket-propelled lifting body spacecraft, air launched from said carrier aircraft and containing in addition to its own propulsion, the payload, staging, propulsion and insertion rocketry necessary to the mission and the provisions for protecting said payload during loading, fueling, transit to and mating with the said carrier aircraft, towing, taxiing, conventional takeoff from the runway, climb and cruise to the selected launch point (LP) and high altitude release, as well as the tracking, navigation and control hardware, software and other equipment to effect a safe, reliable and affordable delivery service, including:

FIGS. 1, 2, 3: Exterior views of LB-1, 1, an unmanned, rocket-powered, wingless lifting body spacecraft, assembled of commercially available composite rocket boosters, complete with solid or hybrid fueled motors and strapping hardware. Said spacecraft's lifting body characteristics are designed to mitigate lift and altitude losses at the horizontal release maneuver (HRM) and its wingless profile allows attachment between engines/landing gear of said carrier aircraft 7. Joined at chine lines 1A & B, streamlined airfoils of carbon/composite form the nose cone, 2A & 2B and main body fairings 3A & 3B to create a strong, lightweight covering and provide a lift factor of approximately 65#/sq ft. 3AA illustrates attachment fairing. Mid-body horizontal chines 1A & 1B on each side gradually widen aft of the nose cone from 2 to 3 feet, terminating in upper and lower “wye” stabilizers 4A & 4B canted outboard 60 degrees from the horizontal and fitted with split elevons 5A & 5B to maintain roll control in the atmosphere. Additionally, the aft chines are fitted with split horizontal elevons 5C for pitch control and use as speed brakes.

Said spacecraft's body cross section may be described as a flattened ellipse with a longitudinally placed, laterally centered conventional ⅔-stage rocket booster flanked by symmetrical pairs of propellant boosters of decreasing diameters and a wide, tapering nose cone to establish the desired cross sectional airfoil.

Four thrusters 6A & 6B have been provided near the forward end of the upper and lower outboard boosters to increase stability during pitch-up. To avoid waste of Stage 1 thrust, small outboard boosters designated “Stage 01” will be ignited to accomplish the pitch-up maneuver prior to Stage 1 ignition. It is foreseen that this combination along with the aforesaid improvement in lift will result in a considerably smoother, more controlled and economical spacecraft rotation.

FIGS. 4, 5, 6: Carrier aircraft belly vertical clearance 7 and landing gear fore and aft clearance 7A & 7B are shown with LB-1 mounted; 7C indicates the coupling keel and 7D the mounting snubbers. Payload bay is at 9, and potential carrier aircraft hard point connections at 10. The arrangement of boosters permitting maximum opportunity to accommodate various loading options and combinations of payload types is shown in relation to stages. The preferred embodiment provides that the rocket casings at 11 may be truncated at the firewall along section line A-A and the entire nose of the spacecraft or selected portions thereof may be utilized.

FIG. 7: A plan view showing a conventional booster display at 13. To enable and control the cost of this “quick-change” facility it is planned that several firewall/payload plate options will be made available at loading sites.

FIG. 8: A plan view provides a positioning diagram for mating of the LB-1 utilizing the carrier aircraft hard point connections 10. An outline of the transport dolly chassis 15 demonstrates lead-in guidance and critical component clearances.

A low, wheeled concave dolly shaped to accept, center and support the convex lower spacecraft half for precisely placing the propellant boosters and to support the same during transit, servicing, fueling, applying the upper spacecraft half and towing under the carrier aircraft for mounting and supplying battery power to said spacecraft components.

Facilities for the monitoring and audible alarm of latching/sealing mechanisms, rising temperatures, leakage of oxidizer, suppression of fire and other safety measures which shall be provided at the spacecraft, and the carrier aircraft cockpit and launch control stations, separate from similar systems in the carrier aircraft.

Attachments and adaptors on the carrier aircraft and the spacecraft to enable the quick attachment/release of said spacecraft.

Facilities in the carrier aircraft and on the ground to remotely control the spacecraft as a mission-abort/reentry vehicle.

Computerized Operations Specifications and irregular and emergency procedures and checklists to be performed by crew members will govern in all phases of the mission.

The LB-1 spacecraft is scalable over the range of potential carrier aircraft to suit the requirements of smaller or larger payloads.

The LB-1 is designed for polar and equatorial launch missions

Although the invention has been described in terms of its preferred embodiment, it is to be understood that many other possible modifications and variations can be made without departing from the spirit and scope of the invention.

Launch preparations, including assembling, loading, and attaching the LB-1 to the aircraft, include, in the following order:

1. Lower body fairing, chines, stabs.

2. Thrust plate.

3. Firewall

4. Stage 2/3 booster.

5. Stage 1 boosters & straps.

6. Stage 01 boosters & straps.

7. Left & Right Thrusters.

8. Payload plate.

9. Upper Body fairing, chines, stabs.

10. Secure cargo in Payload Bay.

11. Place nose cone, secure & check all fasteners.

12. Align LB-1 beneath carrier aircraft.

13. Complete LB-1 attachment checklist.

14. Attach LB-1 to carrier aircraft & secure.

Flight operations, including towing, taxiing, takeoff, and flight, require the following:

1. All towing operations with LB-1 attached shall be conducted in radio contact with qualified ground crew ahead and behind the carrier aircraft and ground level visibility of at least 3 nautical miles.

2. Prior to engine start all landing gear and tires shall be checked for damage or irregularities and the captain advised.

3. Immediately prior to every take-off with LB-1 attached the ground crew shall scan the take off runway for foreign objects and remove any debris advising the captain by radio that the runway surface is safe for takeoff.

4. When the captain receives the ground crew “disconnect” salute his acknowledgement will indicate his acceptance of aircraft, spacecraft and runway surface as suitable for the launch mission subject to tower takeoff clearance, and he will change frequency accordingly. The ground crew will remain clear of the taxiway but in the general area until the takeoff is complete.

5. Special procedures will govern LB-1 flight operations, including more restrictive takeoff weather minimums for ceiling, visibility, crosswind, runway clutter and precipitation. Also rejected takeoff, fuel dumping, primary and alternate launch point (LP) criteria, will be more critical, especially tropopause weather, particularly winds, which can be in excess of 200 knots and turbulence which may be extreme. Alternate launch points (LPs)/altitudes will be filed for every mission.

6. Staging will generally be conventional for the launch type being conducted, however all specifications, exceptions, alternate launch points (LPs) and other advisories will be included on the flight plan and updated automatically or upon request.

7. In the event of a failure in a primary launch system or component, a joint decision will be reached between the captain and the launch coordinator as to whether a safe/successful launch can be achieved with a standby system or component or hand-flown maneuver, or whether the load should be returned to base or jettisoned, and if either of the latter, whether carrier aircraft fuel dumping or another safer course of action is indicated.

8. Although air-launch has demonstrated an excellent safety record in both manned and unmanned missions, payload insurance continues a major driver of launch cost, therefore every effort should be extended to design equipment and procedures to the highest standards of safe operation. 

The inventors claim:
 1. The present invention is a system for launching small satellites, including small-sats, mini-sats, nano-sats, medical and scientific experiments, suborbital, orbital and other aerospace payloads, including a modified and optimized existing carrier aircraft, a streamlined, unmanned rocket-propelled lifting body spacecraft, air launched from said carrier aircraft and containing in addition to its own propulsion, the payload, staging, propulsion and insertion rocketry necessary to the mission and the provisions for protecting said payload during loading, fueling, transit to and mating with the said carrier aircraft, taxiing, conventional takeoff from the runway, climb and cruise to the selected launch point (LP) and high altitude release, as well as the tracking, navigation and control hardware, software and other equipment to effect a safe, reliable and affordable delivery, including:
 2. LB-1, an unmanned, rocket-powered, wingless lifting body spacecraft, assembled of commercially available composite rocket boosters, complete with solid or hybrid fueled motors and strapping hardware, employed to improve the efficiency and lower the gross weight and costs of air launched commercial payloads. Said spacecraft's lifting body characteristics are designed to mitigate lift and altitude losses during the horizontal release maneuver (HRM) and its wingless profile allows attachment between engines/landing gear of said carrier aircraft. Joined at the chine lines, streamlined airfoils of high-temp carbon/composite form the nose cone and main body upper and lower fairings to create a strong, light covering and provide a lift factor of approximately 65#/sq. ft. Said spacecraft's body cross section may be described as a flattened ellipse with a longitudinally placed, laterally centered conventional ⅔-stage rocket booster flanked by symmetrical pairs of propellant boosters of decreasing diameters and a wide, tapering nose cone to establish the desired cross sectional airfoil.
 2. Mid-body horizontal upper and lower chines on each side gradually widen aft of the nose cone from 2 to 3 feet, terminating in upper and lower “wye” stabilizers canted outboard 60 degrees from the horizontal and fitted with split elevons to maintain roll control in the atmosphere. In addition, the aft chines are fitted with split horizontal elevons for pitch control and use as speed brakes. Four thrusters have been provided near the forward end of the upper and lower outboard boosters to increase stability following release. To avoid waste of Stage 1 thrust, small outboard boosters designated “Stage 01” will be ignited to accomplish the pitch-up maneuver prior to Stage 1 ignition. It is foreseen that this combination along with the aforesaid improvement in lift will result in a considerably smoother, more controlled and economical spacecraft rotation. To allow maximum opportunity to accommodate various loading options and combinations of payload types, the preferred embodiment provides that the rocket casings may be truncated at the firewall and the entire spacecraft nose or selected portions thereof may be utilized in place of the usual payload booster nose cone/s. To enable and control the cost of this “quick-change” facility it is planned that several firewall/payload plate options will be made available at loading sites. A plan view showing a positioning and attachment diagram of the LB-1 utilizing the carrier aircraft hard point connections. An outline of the transport dolly chassis illustrates lead-in guidance and critical component clearances.
 3. Another embodiment of the LB-1 will be its use as a flying “Launch Laboratory” for the flight testing and optimizing of other new light-sat vehicles to speed their development, particularly in the field of small-sat constellation building. 